CN112898024A - Wave-absorbing ceramic wing rudder type component based on functional fiber gradient distribution and preparation method thereof - Google Patents
Wave-absorbing ceramic wing rudder type component based on functional fiber gradient distribution and preparation method thereof Download PDFInfo
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Abstract
The invention relates to the field of high-temperature-resistant wave-absorbing structures, and particularly discloses a wave-absorbing ceramic wing rudder type component based on functional fiber gradient distribution, which sequentially comprises the following components from inside to outside: bear sandwich layer, bottom, microwave absorbing layer, surface course, it is continuous carbon fiber reinforcement ceramic matrix composite or continuous low resistivity carborundum fiber reinforcement ceramic matrix composite to bear the sandwich layer, bottom and surface course are high resistivity carborundum fiber reinforcement ceramic matrix composite, the microwave absorbing layer is individual layer carborundum fiber plain weave reinforcing ceramic matrix composite, and each layer composite ceramic matrix is the same, for in carborundum, silicon oxygen carbon, silicon carbon nitrogen, silicon boron nitrogen, boron nitride or the silicon boron carbon nitrogen. The invention also discloses a preparation method of the wave-absorbing ceramic wing rudder type component. The wave-absorbing ceramic wing rudder type component provided by the invention has the integrated functions of high bearing, ablation resistance, strong heat prevention, broadband wave absorption and the like, and can remarkably improve the survival and penetration capability of a new generation of aircraft.
Description
Technical Field
The invention belongs to the field of high-temperature-resistant wave-absorbing structures, and particularly relates to a wave-absorbing ceramic wing rudder component based on functional fiber gradient distribution and a preparation method thereof.
Background
The wing rudder type component is an important component of the aircraft and mainly plays key roles in controlling the stability, regulating and controlling the attitude and the like of the aircraft. Meanwhile, because the radar wave scattering property of wing rudder type components is obvious and is one of strong scattering sources on the aircraft, the aircraft is easy to detect and strike, the radar wave scattering property of the aircraft is reduced by adopting a wave-absorbing material technology, and the survival and penetration capability is improved. With the increase of the speed of the aircraft, the thermal load borne by the wing rudder type component is larger and larger, and for the high-speed aircraft, the wing rudder type component is required to have integrated functions of heat prevention, load bearing, ablation resistance, wave absorption and the like. The existing wing rudder type components of the high-speed aircraft mainly comprise two types: the composite material comprises a metal core layer, a resin-based composite material heat-proof outer layer and a ceramic matrix composite material member.
The wave absorbing function of the metal core layer and the resin-based composite material heat-proof outer layer is mainly realized by adding a radar absorbent into the resin-based composite material heat-proof outer layer, but the structure mainly has the following problems: 1) the uniformity of the material can be obviously influenced by the addition of the absorbent, so that the mechanical and heat-proof properties of the resin-based composite material are influenced; 2) the addition of an absorbent can add significant weight to the component; 3) the addition amount of the absorbent in the composite material is limited, and the broadband wave absorption is difficult to realize due to the electromagnetic parameter dispersion characteristic of the absorbent; 4) the applicability of the component to the high-speed long-term aircraft is poor, the wing rudder of the high-speed long-term aircraft can bear severe thermal load, and the heat-proof outer layer of the resin-based composite material can have a serious ablation problem, so that the appearance of the wing rudder is obviously changed, and the attitude control and guidance precision of the aircraft is seriously reduced. The ceramic matrix composite component has the integrated functions of heat prevention, bearing and ablation resistance, can be applied to high-speed long-term aircrafts with severe thermal load, and at present, the component mainly adopts a continuous carbon fiber reinforced silicon carbide composite material system with high strength characteristic due to large load, but does not have stealth function due to the fact that the high conductivity characteristic of continuous carbon fiber can generate strong scattering to radar waves, and the electromagnetic scattering characteristic is similar to that of a metal component. In conclusion, the prior art schemes are difficult to realize the integrated functions of heat prevention, load bearing, ablation resistance, wave absorption and the like of wing rudder type components of future high-speed long-term aircrafts, and a brand new technical scheme needs to be provided.
Disclosure of Invention
The invention aims to provide a wave-absorbing ceramic wing rudder type component based on functional fiber gradient distribution, which has the integrated functions of heat prevention, load bearing, ablation resistance, wave absorption and the like, and also provides a preparation method of the wave-absorbing ceramic wing rudder type component, so that the defects and shortcomings in the background art are overcome.
In order to achieve the purpose, the invention provides a wave-absorbing ceramic wing rudder type component based on functional fiber gradient distribution, which sequentially comprises the following components from inside to outside: bear sandwich layer, bottom, microwave absorbing layer, surface course, it is continuous carbon fiber reinforcement ceramic matrix composite or continuous low resistivity carborundum fiber reinforcement ceramic matrix composite to bear the sandwich layer, bottom and surface course are high resistivity carborundum fiber reinforcement ceramic matrix composite, the microwave absorbing layer is individual layer carborundum fiber plain weave reinforcing ceramic matrix composite, and each layer composite ceramic matrix is the same, for in carborundum, silicon oxygen carbon, silicon carbon nitrogen, silicon boron nitrogen, boron nitride or the silicon boron carbon nitrogen.
Preferably, in the wave-absorbing ceramic wing rudder type component, the continuous carbon fiber reinforced ceramic matrix composite reinforcement is a needle punched fabric, a sewn fabric, a 2.5D carbon fiber fabric and a 3D carbon fiber fabric, copper rods with the diameter of 1-1.2 mm are implanted into the fabric, the axial direction of the copper rods is parallel to the thickness direction of the fabric, the copper rods are arranged in a square array, and the axial center distance of the copper rods in the transverse and longitudinal directions is 10-15 mm.
Preferably, in the wave-absorbing ceramic wing rudder type component, the continuous low-resistivity silicon carbide fiber reinforced ceramic matrix composite reinforcement is a needle punched, sewn, 2.5D or 3D silicon carbide fiber fabric, the resistivity of the silicon carbide fiber is lower than 0.1 Ω · cm, copper rods with the diameter of 1-1.2 mm are implanted into the fabric, the axial direction of the copper rods is parallel to the thickness direction of the fabric, the copper rods are arranged in a square array, and the axial distance between the horizontal and vertical axes of the copper rods is 10-15 mm.
Preferably, in the wave-absorbing ceramic wing rudder type component, the high-resistivity silicon carbide fiber reinforced ceramic matrix composite reinforcement is a needled, sewn, 2.5D or 3D silicon carbide fiber fabric, and the silicon carbide fiber resistivity is greater than 105Omega cm, and the surface of the fiber contains a boron nitride coating with the thickness of 0.1-0.3 μm.
Preferably, in the wave-absorbing ceramic wing rudder type component, the square resistance of the wave-absorbing layer silicon carbide fiber plain cloth is 80-150 omega/sq, and the thickness is 0.3-0.4 mm.
The preparation method of the wave-absorbing ceramic wing rudder type component comprises the following steps:
(1) preparing a fiber woven part by reserving allowance for carbon fiber or silicon carbide fiber meeting requirements according to the design size of a component, then implanting a copper rod with the diameter of 1-1.2 mm into the fabric, wherein the axial direction of the copper rod is parallel to the thickness direction of the fabric, taking a silicon carbide, silicon-oxygen-carbon, silicon-carbon-nitrogen, silicon-boron-nitrogen, boron nitride or silicon-boron-carbon-nitrogen organic precursor solution as a dipping solution, and carrying out dipping, high-temperature cracking and repeated densification on the fiber woven part by adopting a precursor dipping cracking process to finish the preparation of a rough blank of a bearing core layer;
(2) according to the size requirement of the bearing core layer, machining the rough blank of the bearing core layer according to the design size to obtain the bearing core layer;
(3) putting the bearing core layer into a nitric acid solution, and completely corroding the copper rod, so that a seaming hole is formed in the bearing core layer; repeatedly washing the bearing core layer with clean water until the cleaning water is colorless and neutral, and drying for 2-4 h at 150 ℃; a copper bar mode is adopted to form a sewing hole, so that damage to the bearing core layer caused by mechanical punching is avoided;
(4) preparing a bottom layer silicon carbide fiber woven piece, a surface layer silicon carbide fiber woven piece and wave-absorbing layer silicon carbide fiber plain cloth which meet the requirements of thickness and electrical property;
(5) from the bearing core layer, paving a bottom layer silicon carbide fiber woven piece, a wave-absorbing layer silicon carbide fiber plain cloth and a surface layer silicon carbide fiber woven piece on symmetrical layers on two surfaces of the bearing core layer, adjusting the position of the bottom layer silicon carbide fiber woven piece, fixing the wave-absorbing layer silicon carbide fiber plain cloth and the surface layer silicon carbide fiber woven piece by adopting a weaving tool, sewing silicon carbide fibers on the bearing core layer through sewing holes in the bearing core layer in an overlapped area with the bearing core layer, sewing the silicon carbide fibers into a whole by adopting the silicon carbide fibers in a non-overlapped area, and finishing the preparation of;
(6) taking the same organic precursor solution in the step (1) as a dipping solution, and adopting a precursor dipping and cracking process to dip, crack at high temperature and densify repeatedly the fiber woven piece to finish the preparation of a component rough blank;
(7) machining the component rough blank to a design size;
(8) and (3) taking the same organic precursor solution as the impregnation solution in the step (1), continuously impregnating, pyrolyzing and repeatedly densifying the component rough blank obtained in the step (7) by adopting a precursor impregnation cracking process, and densifying to obtain the component.
Preferably, in the above preparation method, in the step (1), the mass content of the precursor in the precursor dipping solution is not less than 40%; the parameters of the impregnation cracking process are as follows: the vacuum impregnation time is not less than 4h, and the pressure is not more than-0.09 MPa; the pyrolysis temperature is 800-1200 ℃, the pyrolysis atmosphere is inert atmosphere, and the time is 0.5-1 h; the densification time is not less than 10 times.
Preferably, in the above preparation method, in the step (5), the resistivity of the silicon carbide fiber used for sewing is greater than 105Omega cm; the sewing density of the fiber weaving piece in the non-overlapping area is 4-16 needles/cm2。
Preferably, in the above preparation method, in the step (6), the impregnation cracking process parameters are as follows: the vacuum impregnation time is not less than 4h, and the pressure is not more than-0.09 MPa; the pyrolysis temperature is 800-1000 ℃, the pyrolysis atmosphere is inert atmosphere, and the time is 0.5-1 h; the number of densification is 6-8.
Preferably, in the above preparation method, in the step (8), the impregnation cracking process parameters are as follows: the vacuum impregnation time is not less than 4h, and the pressure is not more than-0.09 MPa; the pyrolysis temperature is 800-1000 ℃, the pyrolysis atmosphere is inert atmosphere, and the time is 0.5-1 h; the number of densification is 3-4.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention provides a structural mode of a wave-absorbing ceramic wing rudder type component based on functional fiber gradient distribution, which can realize the integrated functions of heat prevention, load bearing, ablation resistance and wave absorption, and takes a continuous carbon fiber reinforced ceramic matrix composite or a continuous low-resistivity silicon carbide fiber reinforced ceramic matrix composite as a load bearing core layer, the material has the characteristics of high temperature resistance and high strength, and can endow the wing rudder type component with strong load bearing function; the silicon carbide fiber reinforced ceramic matrix composite with the gradient distribution of the resistivity has the characteristics of high temperature resistance, high strength, oxidation resistance and low thermal conductivity, and meanwhile, the material can realize impedance matching and loss of radar waves in a wide frequency band range and has a wide frequency wave absorbing function.
2. The wave-absorbing ceramic wing rudder member has good thermophysical property matching of materials of all layers, realizes integrated integral molding by adopting a process mode of fiber sewing and subsequent densification, and has the advantages of good integrity, high interlayer bonding strength and excellent comprehensive mechanical property.
3. The wing rudder type structure based on functional fiber gradient distribution can solve the problem of the traditional technical scheme, can be applied to high-speed long-term aircrafts, has the integrated functions of high bearing capacity, ablation resistance, strong heat prevention, broadband wave absorption and the like, and can remarkably improve the survival and penetration capability of the new-generation aircrafts.
Drawings
FIG. 1 is a schematic structural view of a wave-absorbing ceramic wing rudder type component in the invention.
Figure 2 is a green carrier core prepared according to the present invention in example 1.
Figure 3 is a photograph of a green carrier core prepared in example 1 of the present invention after processing.
FIG. 4 is a photograph of a copper rod bearing a core prepared in example 1 of the present invention after etching.
Fig. 5 is a photograph of a member knit prepared in example 1 of the present invention.
Fig. 6 is a photograph of the wave-absorbing ceramic wing rudder type component prepared in the embodiment 1 of the present invention.
Description of the main reference numerals:
1-bearing core layer, 2-bottom layer, 3-wave absorbing layer and 4-surface layer.
Detailed Description
The following detailed description of specific embodiments of the invention is provided, but it should be understood that the scope of the invention is not limited to the specific embodiments.
Example 1
A wave-absorbing ceramic wing rudder type component based on functional fiber gradient distribution is shown in figure 1 and sequentially comprises from inside to outside: the continuous carbon fiber reinforced ceramic matrix composite material comprises a bearing core layer 1, a high-resistivity silicon carbide fiber reinforced ceramic matrix composite material bottom layer 2 (with the thickness of 2.5 mm), a single-layer silicon carbide fiber plain cloth reinforced ceramic matrix composite material wave-absorbing layer 3, a high-resistivity silicon carbide fiber reinforced ceramic matrix composite material surface layer 4 (with the thickness of 2.5 mm), and all layers of composite material ceramic matrixes are made of silicon carbide. The continuous carbon fiber reinforced ceramic matrix composite reinforcement is a sewn carbon fiber fabric, copper bars with the diameter of 1mm are implanted into the fabric, the axial direction of the copper bars is parallel to the thickness direction of the fabric, the copper bars are arranged in a square array, and the axial center distance of the copper bars in the transverse and longitudinal directions is 10 mm. The reinforcements in the bottom layer and the surface layer of the high-resistivity silicon carbide fiber reinforced ceramic matrix composite material are sewn silicon carbide fiber fabrics, and the resistivity of the silicon carbide fibers is 5 multiplied by 105Ω · cm and the fiber surface contained a 0.2 μm thick coating of boron nitride. The square resistance of the plain weave of the silicon carbide fiber of the wave-absorbing layer is 120 omega/sq, and the thickness is 0.35 mm.
The embodiment also provides a preparation method of the wave-absorbing ceramic wing rudder type component based on the gradient distribution of the functional fibers, which comprises the following steps:
(1) the carbon fiber meeting the requirements is prepared into a fiber woven part by reserving allowance according to the design size of a component, then a copper rod with the diameter of 1mm is implanted into the fabric, the axial direction of the copper rod is parallel to the thickness direction of the fabric, polycarbosilane xylene solution is used as precursor impregnation solution, the mass content of polycarbosilane in the precursor impregnation solution is 50%, a precursor impregnation cracking process is adopted to impregnate, pyrolyze and repeatedly densify the fiber woven part, and the impregnation cracking process parameters are as follows: the vacuum impregnation time is 6h, and the pressure is-0.095 MPa; the pyrolysis temperature is 1200 ℃, the pyrolysis atmosphere is high-purity nitrogen, and the time is 0.5 h; densifying for 12 times to complete the preparation of the rough blank of the bearing core layer (figure 2);
(2) according to the size requirement of the bearing core layer, machining the rough blank of the bearing core layer to enable the size of the bearing core layer to meet the requirement, wherein FIG. 3 is a photo of the rough blank of the bearing core layer after machining;
(3) putting the bearing core layer into a nitric acid solution, and completely corroding the copper rod, so that suture holes are formed in the bearing core layer as shown in figure 4; repeatedly washing the bearing core layer with clear water until the washing water is colorless and neutral, and drying for 4h at 150 ℃;
(4) preparing a bottom layer silicon carbide fiber woven piece, a surface layer silicon carbide fiber woven piece and wave-absorbing layer silicon carbide fiber plain cloth which meet the requirements of thickness and electrical property;
(5) from the bearing core layer, spreading a bottom layer silicon carbide fiber woven piece, a wave-absorbing layer silicon carbide fiber plain cloth and a surface layer silicon carbide fiber woven piece on symmetrical layers on two surfaces of the bearing core layer, adjusting the positions of the silicon carbide fiber woven piece, the wave-absorbing layer silicon carbide fiber plain cloth and the surface layer silicon carbide fiber woven piece by adopting a weaving tool, and adopting the area with the overlapping area of the silicon carbide fiber woven piece and the bearing core layer and the specific5The silicon carbide fiber of omega cm is sewed on the bearing core layer through the sewing holes on the bearing core layer, the weaving piece of the non-overlapping area adopts the structure that the resistivity is 5 multiplied by 105The silicon carbide fiber of omega cm is sewed into a whole, and the sewing density of the fiber weaving piece in the non-overlapping area is 9 needles/cm2Completing the preparation of the component mat, which is depicted in fig. 5;
(6) taking the same organic precursor solution in the step (1) as a dipping solution, and adopting a precursor dipping and cracking process to dip, crack at high temperature and densify repeatedly the fiber woven piece, wherein the parameters of the dipping and cracking process are as follows: the vacuum impregnation time is 6h, and the pressure is-0.095 MPa; the high-temperature cracking temperature is 900 ℃, the cracking atmosphere is high-purity nitrogen, and the time is 1 h; densifying for 8 times to finish the preparation of component rough blank;
(7) machining the component rough blank to a design size;
(8) taking the same organic precursor solution in the step (1) as a dipping solution, and continuously dipping, pyrolyzing and repeatedly densifying the component rough blank obtained in the step (7) by adopting a precursor dipping and cracking process, wherein the parameters of the dipping and cracking process are as follows: the vacuum impregnation time is 6h, and the pressure is-0.095 MPa; the high-temperature cracking temperature is 900 ℃, the cracking atmosphere is high-purity nitrogen, and the time is 1 h; densifying for 4 times to obtain the wave-absorbing ceramic wing rudder type component.
Fig. 6 is a photo of the wave-absorbing ceramic wing rudder component prepared in this embodiment, which has excellent integrated functions of high load bearing, strong heat protection, broadband wave absorption and the like, and the scattering characteristic of the C, X, Ku frequency band radar can be reduced by more than 8dB compared with that of metal.
The foregoing descriptions of specific exemplary embodiments of the present invention have been presented for purposes of illustration and description. It is not intended to limit the invention to the precise form disclosed, and obviously many modifications and variations are possible in light of the above teaching. The exemplary embodiments were chosen and described in order to explain certain principles of the invention and its practical application to enable one skilled in the art to make and use various exemplary embodiments of the invention and various alternatives and modifications as are suited to the particular use contemplated. It is intended that the scope of the invention be defined by the claims and their equivalents.
Claims (10)
1. The wave-absorbing ceramic wing rudder type component based on functional fiber gradient distribution is characterized by comprising the following components from inside to outside in sequence: bear sandwich layer, bottom, microwave absorbing layer, surface course, it is continuous carbon fiber reinforcement ceramic matrix composite or continuous low resistivity carborundum fiber reinforcement ceramic matrix composite to bear the sandwich layer, bottom and surface course are high resistivity carborundum fiber reinforcement ceramic matrix composite, the microwave absorbing layer is individual layer carborundum fiber plain weave reinforcing ceramic matrix composite, and each layer composite ceramic matrix is the same, for in carborundum, silicon oxygen carbon, silicon carbon nitrogen, silicon boron nitrogen, boron nitride or the silicon boron carbon nitrogen.
2. The wave-absorbing ceramic wing rudder member according to claim 1, wherein the continuous carbon fiber reinforced ceramic matrix composite reinforcement is a needle punched, sewn, 2.5D or 3D carbon fiber fabric, copper rods with the diameter of 1-1.2 mm are implanted in the fabric, the axial direction of the copper rods is parallel to the thickness direction of the fabric, the copper rods are arranged in a square array, and the axial center distance of the copper rods in the transverse and longitudinal directions is 10-15 mm.
3. The wave-absorbing ceramic wing rudder component according to claim 1, wherein the continuous low-resistivity silicon carbide fiber-reinforced ceramic matrix composite reinforcement is a needle punched, sewn, 2.5D or 3D silicon carbide fiber fabric, the resistivity of the silicon carbide fiber is lower than 0.1 Ω -cm, copper rods with the diameter of 1-1.2 mm are implanted in the fabric, the axial direction of the copper rods is parallel to the thickness direction of the fabric, the copper rods are arranged in a square array, and the axial center distance of the copper rods in the transverse and longitudinal directions is 10-15 mm.
4. The wave-absorbing ceramic wing rudder type component according to claim 1, wherein the high-resistivity silicon carbide fiber reinforced ceramic matrix composite reinforcement is a needle punched, sewn, 2.5D, 3D silicon carbide fiber fabric, and the silicon carbide fiber resistivity is greater than 105Omega cm, and the surface of the fiber contains a boron nitride coating with the thickness of 0.1-0.3 μm.
5. The wave-absorbing ceramic wing rudder type component according to claim 1, wherein the wave-absorbing layer silicon carbide fiber plain weave cloth square resistance is 80-150 Ω/sq, and the thickness is 0.3-0.4 mm.
6. The preparation method of the wave-absorbing ceramic wing rudder member according to any one of claims 1 to 5, characterized by comprising the following steps:
(1) preparing a fiber woven part by reserving allowance for carbon fiber or silicon carbide fiber meeting requirements according to the design size of a component, then implanting a copper rod with the diameter of 1-1.2 mm into the fabric, wherein the axial direction of the copper rod is parallel to the thickness direction of the fabric, taking a silicon carbide, silicon-oxygen-carbon, silicon-carbon-nitrogen, silicon-boron-nitrogen, boron nitride or silicon-boron-carbon-nitrogen organic precursor solution as a dipping solution, and carrying out dipping, high-temperature cracking and repeated densification on the fiber woven part by adopting a precursor dipping cracking process to finish the preparation of a rough blank of a bearing core layer;
(2) according to the size requirement of the bearing core layer, machining the rough blank of the bearing core layer according to the design size to obtain the bearing core layer;
(3) putting the bearing core layer into a nitric acid solution, and completely corroding the copper rod, so that a seaming hole is formed in the bearing core layer; repeatedly washing the bearing core layer with clean water until the cleaning water is colorless and neutral, and drying for 2-4 h at 150 ℃;
(4) preparing a bottom layer silicon carbide fiber woven piece, a surface layer silicon carbide fiber woven piece and wave-absorbing layer silicon carbide fiber plain cloth which meet the requirements of thickness and electrical property;
(5) from the bearing core layer, paving a bottom layer silicon carbide fiber woven piece, a wave-absorbing layer silicon carbide fiber plain cloth and a surface layer silicon carbide fiber woven piece on symmetrical layers on two surfaces of the bearing core layer, adjusting the position of the bottom layer silicon carbide fiber woven piece, fixing the wave-absorbing layer silicon carbide fiber plain cloth and the surface layer silicon carbide fiber woven piece by adopting a weaving tool, sewing silicon carbide fibers on the bearing core layer through sewing holes in the bearing core layer in an overlapped area with the bearing core layer, sewing the silicon carbide fibers into a whole by adopting the silicon carbide fibers in a non-overlapped area, and finishing the preparation of;
(6) taking the same organic precursor solution in the step (1) as a dipping solution, and adopting a precursor dipping and cracking process to dip, crack at high temperature and densify repeatedly the fiber woven piece to finish the preparation of a component rough blank;
(7) machining the component rough blank to a design size;
(8) and (3) taking the same organic precursor solution as the impregnation solution in the step (1), continuously impregnating, pyrolyzing and repeatedly densifying the component rough blank obtained in the step (7) by adopting a precursor impregnation cracking process, and densifying to obtain the component.
7. The preparation method according to claim 6, wherein in the step (1), the mass content of the precursor in the precursor impregnation solution is not less than 40%; the parameters of the impregnation cracking process are as follows: the vacuum impregnation time is not less than 4h, and the pressure is not more than-0.09 MPa; the pyrolysis temperature is 800-1200 ℃, the pyrolysis atmosphere is inert atmosphere, and the time is 0.5-1 h; the densification time is not less than 10 times.
8. The method according to claim 6, wherein in the step (5), the resistivity of the silicon carbide fiber used for sewing is greater than 105Omega cm; the sewing density of the fiber weaving piece in the non-overlapping area is 4-16 needles/cm2。
9. The preparation method according to claim 6, wherein in the step (6), the impregnation cracking process parameters are as follows: the vacuum impregnation time is not less than 4h, and the pressure is not more than-0.09 MPa; the pyrolysis temperature is 800-1000 ℃, the pyrolysis atmosphere is inert atmosphere, and the time is 0.5-1 h; the number of densification is 6-8.
10. The preparation method according to claim 6, wherein in the step (8), the impregnation cracking process parameters are as follows: the vacuum impregnation time is not less than 4h, and the pressure is not more than-0.09 MPa; the pyrolysis temperature is 800-1000 ℃, the pyrolysis atmosphere is inert atmosphere, and the time is 0.5-1 h; the number of densification is 3-4.
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